Water launched missile



March 29, 1966 A. E. LA POINTE 3,242,810

WATER LAUNCHED MISSILE Filed Sepi. 27, 1962 5 Sheets-Sheet l 105 IO 03 l 57 7| 6| 59 INVENTOR.

ANDRE E. LO POINTE AGENT.

March 29, 1 A. E. LA POINTE WATER LAUNCHED MISSILE 5 Sheets-Sheet 2 Filed Sept. 27, 1962 March 29, 1966 A. E. LA POINTE WATER LAUNCHED MI S S ILE 5 Sheets-Sheet 5 Filed Sept. 27, 1962 Ivm hmm

INVENTOR.

ANDRE E. LGPOINTE AGENT.

March 29,1966 A. E. LA POINTE WATER LAUNCHED MISSILE 5 Sheets-Sheet 4.

Filed Sept. 27, 1962 FIG.4.

INVENTOR.

ANDRE E. La POINTE lOG HyLEVEL SWITCH & X 103 \01 BY W @W FIG.5.

AGENT March 29, 1966 A. E. LA POlNTE 3,242,810

WATER LAUNCHED MISSILE Filed Sept. 27, 1962 5 Sheets-Sheet 5 FIG.6.

FIG.7.

FIG. II.

INVENTOR.

ANDRE E. LCIPOINTE FIG. 9. BY May w.

AGENT.

United States Patent 3,242,810 WATER LAUNCHED MISSILE Andre E. La Pointe, Montgomery County, Md, assignmto the United States of America as represented by the Secretary of the Navy Filed Sept. 27, 1962 Ser. No. 227,663 24 (Ilairns. (Cl. 89-1.7)

The invention described herein may be manufactured and used by or for the Government of the United States of America for governmental purposes without the payment of any royalties thereon or therefor.

This invention relates to a water launched missile and more particularly to a missile for dispersing radar reflective material in the atmosphere at a predetermined time after launching from either a surface or submerged station.

Numerous arrangements have been implemented for the dispersing of radar reflective material (sometimes referred to as window) either from airborne or from surface stations In the prior art, arrangements for launching and releasing window have been limited specifically to the environment and characteristics of the launching station. It would be highly desirable to provide means for launching and dispersing window which is of a basic design and which may be easily adapted for launching from stations of different types and in different environments.

Accordingly, it is an object of the present invention to provide a window-dispersing missile which may be launched from stations located either :on or beneath the surface of water,

Another object of the invention is to provide a Water launched missile for dispersing material into the atmosphere at some predetermined time after the missile has been launched from its launching station.

Another object of this invention is to provide a window dispersing missile capable of being launched from either a submerged or surface station is essentially the same manner and with a minimum of adjustments.

Yet another object of this invention is to provide a simple, reliable and inexpensive window dispersing missile of a basic design which may be easily adapted for launching for surface or submerged stations.

A feature of the present invention is the provision of means attachable to a basic missile launching unit for adapting said unit for launching from a subsurface station such as a submarine.

Another feature of this invention is the provision of novel thrust producing means for controllably projecting a window-containing missile to a predetermined altittude.

These and other objects, features and advantages of the present invention will be better understood by referring to the accompanying drawings in which like numerals are use to represent like parts and in which:

FIGS. 1, 2 and 3 are view in longudinal cross of various portions of a missile launching unit according to the invention;

FIG. 4 is a view in perspective of a portion of the missile launching unit according to the invention in a flotation position;

FIG. 5 is a simplified schematic circuit diagram of an embodiment of the wiring system for the missile launching unit according to the invention; and

FIGS. 6l2 are diagrammatic views of the missile launching unit according to the invention in various stages of operation.

The illustrated embodiment of the invention shown in FIGS. 1 and 2 taken together represent the missile launching unit adapted for launching from a submarine or other subsurface station. FIG. 1 represents the lower or rearward end, and FIG. 2, the upper or forward end of the missile launching. The subsurface launching unit of FIGS. 1 and 2 includes a missile control unit 9 and a subsurface launched control unit 11 tandemly attachable to the forward (i.e., left) end of the unit 9. The missile control unit 9 has a timing ejection control section 12 and a watertight missile firing section 13, both of which are mounted in an outer cylindrical casing or container 15. The lower or rearward end of the casing 15 (at the right in FIG. 1) has a thick inwardly protruding annular shoulder 17 with an inside annular groove 19. The lower end of the casing 15 houses the ejection timing control unit 12 which will now be described.

The unit 12 includes a hollow cylindrical knob rotor 21 having an outwardly extending flange 23 in rotating sliding engagement with the inner surface of the shoulder 17. The rotor 21 is held axially in place by an annular key 25 which fits snugly in the annular groove 19 and bears against the flange portion 23 of the knob rotor 21. An index or timing setting ring 27 is rigidly attached to the knob rotor 23 by means of a radial retaining screw 29 so that the index ring 27 and rotor 21 rotate in unison. An array of scale gradations 31 is suitably located on the outer surface of the casing 15 adjacent the ring 27 so that the index ring may be rotated to a predetermined time scale setting.

A timer key 33 in the form of a cylindrical body 35, having a hollow interior portion 37 cruciform in transverse cross section, fits loosely inside the hollow portion of the knob rotor 21. The timer key 33 also has an axial control shaft 39 extending upwardly to a slightly protruding bulbous portion 41. At the greatest diameter 'of the bulbous portion 41 there is a transverse hole 43 for receiving parts of ball bearings 45 and 47 respectively. The bearings 45 and 47 are too large in diameter to fit completely into the transverse hole 43.

A link element 49, cruciform in transverse cross section, fits in longitudinal sliding engagement into the cruciform shaped hollow interior portion 37 of the timer key 33. Each leg of one opposing pair of legs 51 of the link element 49 is circular in cross section and extends transversely through the hollow portion 37 into a longitudinal recess 53 located in the knob rotor 21. Each of the other pair of legs 55 of the cruciform shaped link element 49 is rectangular in cross section and fits into opposing hollow portions of the interior portion 37. Thus, when the knob rotor 21 is turned with the index ring 27 to a scale setting, the bulbous portion of the control shaft 39 is rotated through the timer key 33-link element 49 linkage.

A watertight timing unit casing 57, cylindrical in shape and of varying inside and outside diameter, is positioned for loose sliding engagement within the outer casing 15 for longitudinal movement therein. An annular base block 59 of varying longitudinal cross-section in press fitted into the lower or back end of the missile timing unit casing 57 and is suitably sealed therewith by means of and O-ring 61. A circular timing base plate 63 has an integral axis shaft 65 extending backwardly into the center opening of the annular base block 59 for support thereby. The rearwardmost end of the shaft 65 is hollowed out to form a cylindrical recess 67 which fits around the bulbous portion 41 of the axial shaft 39. The shaft 65 has a pair of opposed transverse radial openings 69 into each of which one of the respective ball bearings 45, 47 normally partially extend. The rear face of the block 59 is tapered inwardly to its central opening forming a tapered portion 6% located adjacent the openings 69. The diameter of each of the ball bearings 45, 47 is greater than the radial length of each of the transverse slots or openings 69, so that the inside surfaces of the central opening of the annular base block 59 bear against each of the ball bearings thus forcing them partially into the transverse hole 43 of the bulbous portion 41 of control shaft 39. Thus, when the axial control shaft 39 is rotated, the shaft 65 through .1? the ball bearing linkage just described is constrained to rotate therewith.

It is to be understood that under the effect of a force tending to pull the shafts 39 and 65 away from each other, the respective ball bearings 45, 47 will each be forced outwardly into and partially through the openings 69 so that the tapered portion 69a bears against each ball bearing thus freeing the shaft 65 from the movement with the control shaft 39. Once the control shaft 39 has been rotated to set the shaft 65 in a certain or given position, the shaft 65 will remain where set after the shafts 39 and 65 have been separated. Moreover, the watertight timer casing 57 remains watertight after said shaft separation.

The index ring 27 is located in a Zero setting by means of a light stop which includes a stop pin 68 secured to and longitudinally extending forward from the edge of the timer key 33. The pin moves with the key 33 in an annular groove 68a in the rear of the base block 59, and when the index ring 27 is rotated clockwise to a zero setting, the pin 68 impinges against a stop bar 70 located radially across the annular groove 68a.

An annular springplate 71 having a short axial shaft portion 73 and a small annular shoulder 75 at the rearmost end of the shaft portion is loosely positioned so that said shaft and shoulder portions are within an annular recess 77 in the forward end of the base block 59. A link rod 79 anchored in the timing base plate 63 extends longitudinally rearward therefrom slidably through the springplate 71 and partially into the outer part of the annular recess 77 for positioning the springplate and for causing the springplate to rotate in unison with the timing base plate 63.

A compression spring 81 is positioned so that its rearwardmost portion is located in the recess 77 urging against the small annular shoulder 75 and its forward end urging against the back of the timing base plate 63. The spring 81 serves to trigger the timing base plate 63 for forward movement in its timer casing 57 when the shafts 39 and 65 are freed from each others movements.

A clock motor 83 of conventional construction is mounted around a central spindle 85, the various gears of the clock escapement (not all of which are shown or indicated specifically) being conveniently supported in any suitable manner by longitudinal spindles anchored in the timing base plate 63. The central spindle is rotatably mounted at its rearward end in an axial recess 87 in the base plate 63 and at its forward end in a support plate 89. The final gear of the clock escapernent, indicated at 91, drives the spindle 85. A transversely extending timing bar 93 is mounted at the forward end of the central spindle 85 for rotation therewith.

Escapement in the clock motor 83 is prevented until a desired time of actuation thereof by means of a thin longitudinal restraining rod 95 passing through an aperture in the timing plate 63. The rod 95 is anchored at its rearmost end in the springplate 71 and at its forwardmost end bears against one of the gears, for example, a gear 97, of the clock motor. When the compression spring 31 is caused to push the timing base plate 63 forward, the gear 97 will be free of the restraint of the rod 95 thus enabling the escapement of the clock motor to rotate the timing bar 93. Longitudinal link rods rigidly connect the support plate 89 to the timing base plate 63 so that they rotate together.

A longitudinal striker rod 99 shown in its position before actuation is mounted at the end of the timing bar 93. A microswitch 101 having a normally open contact arm 103 is located in the housing 57 just forward of the sweep of the striker rod 99 before actuation of the striker rod. However, when the clock is actuated, the sweep of the striker rod will be moved longitudinally forward sufficiently far so that the rod will eventually impinge upon the contact arm 103 to close the microswitch circuit.

Referring to FIG. 5, the simplified embodiment of the rnicroswitch circuit is shown in schematic form, and includes, as labeled, a sea battery 105, the microswitch 101 and a mercury level switch 106 all connected in series with a glow plug 107.

As shown in FIG. 1 the sea battery 105 is annular in shape and mounted in surrounding relationship to a smaller diameter portion of the timing casing 57. Watertightly sheathed leads from the battery 105 (not shown) may be passed in any suitable manner through the walls of the casing 57 for connection to the microswitch and mercury level switch according to the schematic of FIG. 5.

The microswitch 101 is suitably mounted on a transverse bulkhead 109 and fastened thereto by means of a nut 111. The mercury level switch 106 may be of wellknown design and is not shown in detail, it being understood that the series circuit shown in FIG. 5 will not energize the glow plug 107 until the mercury level switch, and hence the missile firing unit 13, is oriented in a level or approximately level position. Other suitable levelactuated switch means may be used in place of the mercury level switch, of course. Care should be taken in the assembly of the missile firing unit 13 so that the mercury level switch 1% will not close the glow plug circuit until the said unit is exactly plumb.

The mercury level switch is contained in a cylindrical casing 113 which is suitably rigidly secured to a flange or shoulder portion 115 of the timer casing 57.

A powerful ejection compression spring 117 is positioned longitudinal inside the casing 15, the rearwardmost end of the compression spring abutting the shoulder portion 17 of the casing 15 and the forwardmost end of the spring 117 abutting against the flange portion 115 of the timer casing. The purpose of the ejection spring 117 is to eject the missile firing unit 13 out of the casing 15. In a working model launching unit according to the invention, wherein the outer casing 15 had a diameter of about three inches, the compression spring 117 was selected to exert a force of about 100 pounds on the flange 115.

A powder cup 119 is press fitted and suitably watertightly sealed into the forward end of the timer casing 57. The powder cup 119 is of varying cross section and has a thick circular base portion 121 and a cup portion 123 having thick walls 125 located forwardly of said base portion. The thick walls 125 define a space 127 having a transverse cardboard partition 128. A quantity of black powder 129 or any other suitable type of explosive material is placed between the partition 128 and the cup base 121. The glow plug 107 referred to in conjunction with FIG. 5 protrudes longitudinally into the powder 129 so that when the microswitch 101 and the mercury level switch 106 are actuated, current from the sea battery 105 energizes the glow plug causing the explosive material 129 to be ignited.

The powder cup 119 is secured at its forward end by means of screws 131 to a barrel 133 and to a chemical cup 135, and the powder cup is suitably sealed with the barrel 133 by means of an O-ring 137.

The explosive force developed in the space or explosion chamber 127 supplies the force to actuate a firing pin 139. The firing pin 139 employs a long stud member 141 threaded at its aftermost end for tight fitting reception into a threaded recess 143 in the powder cup 119. The firing pin has a reduced diameter portion, double concave in longitudinal cross-section, so that it forms a neck 145 in its narrowest region. Forward of the narrow neck portion 14-5 is a thicker diameter portion 147 forming a shoulder Ti -l9. The forward end of the stud member 139 is threaded to receive a firing pin nut 151. A pointed firing pin 153 is suitably mounted axially in the forwardrnost end of the stud member 139 and protrudes therefrom.

It is understood that when the explosion occurs in the space 127, only the fully developed force of the explosion is sufiicient to sever the narrow neck portion 145 of the stud member 139 thereby pushing the stud member for-.

ward. The proportions of the neck 145 thus serve as a controlling factor for predetermining the explosive force to "be applied to the window-containing missile to be launched.

A push block 155 in the form of a thick annulus has a hole in its center for supporting the firing stud member 139 in its axial position. The push block 155 supports a window-containing missile 156. An O-ring 157 provides a seal between the push block 155 and the stud member 139. The push block 155 also has a longitudinally forwardly extending ring portion 158 integral therewith. A spacer ring 61 bears on its longitudinal forward face against the push block 155 and on its rearward face against the powder cup 119.

It will be appreciated that when the explosion occurs in the chamber or space 127, the shoulder 147 of the forwardly moving stud member 139 of the firing pin strikes against the push block 155. The push block is moved longitudinally forward with considerable force due to direct force of the explosion in the chamber 12? acting against the rearward surface of the push block 155 itself. The explosion and resulting forward motion of the push block 155 provides thrust-producing means for launching of the window-containing missile.

The window-containing missile 156 has a base portion (shown at the left of FIG. 1) and includes a thick annul ar base ring 159 suitably bonded, Welded, or press fitted into a thick annular base block 161 having a rearward portion 163 of diameter slightly reduced below that of its thicker diameter portion 165. The base ring 159 is of about the same diameter as that of the thicker diameter portion 165 of the base block 161.

In the recess 167 thus formed between the base ring 159 and the portion 164 are mounted four spring biased fins 169 each having a circular surface to conform with the shape of the recess 167 for containment within. Each of the fins 169 is biased by a torsion spring 171 of conventional construction mounted on a hinge 1'73 extending longitudinally along the recess 167 and supporting each of the respective fins 169. The ring portion 153 of the push block 155 serves to restrain the fins 169 from outward movement until the missile 157 is pushed away therefrom.

The base block 161 has in its rearwardmost central portion a cylindrically shaped recess 175 whose inner surfaces surround but are spaced from the firing pin nut 151 and the firing pin 153. In the opposite end of the base block 161 from the recess 175 is a forward cylindrically shaped recess 177 coaxial therewith having a deeper threaded portion 179. The threaded portion 179 receives a hollow explosion nut 151 having radial apertures 182. The nut 181 is of dimensions sufficiently smaller than those of the forward recess 177 so that an essentially annular chamber 183 is formed having fiuid communication with the inner hollow confines of the nut 181 via the radial apertures 182 thereof.

The hollow portion of the nut 181 includes an axial bore 185 in spatial communication with the radial apertures 182. The base block 161 has an axial bore 187 of the same diameter as the bore 185 of the nut 181. The bore 187 spatially connects the recess 175 and 183. A sleeve 189 of variable dimensions to be selected as desired is located axially in the bore 187, and the axial bore of the sleeve 189 is filled with a controllably burnable or explosive material such as black powder and the like to form a pyrotechnic delay line 191. The hollow portion of the nut 181 is filled with explosive material such as smokeless powder so that when the firing pin 153 strikes the explosive material of the delay line 191, in the rearmost regioin of the sleeve 189, said material will burn in the forward direction thus eventually causing the explosive material in the hollow confines of the nut 181 to explode.

The window-containing missile 156 has a cylindrical outer casing 193, the rearwardmost end of which is press seal between the ogive 201 and the shoulder 205.

fitted into the thick diameter portion of the base block 161. A window-material supporting base plate in the form of a circular disc is mounted in the casing 193 for sliding longitudinal movement therein. A pair of half-sleeves 197 each in the form of a hollow half-cylinder are each releasably fitted into the edge of the base plate 195 for slidable movement therewith inside the outer missile casing 193. Conventional filamentary radar refiective material 199 is placed in any convenient form and manner inside of the half-sleeves 197. Of course, any other material having useful purpose when dispersed or released into the atmosphere may be used in place of the radar reflective material or window 199 if desired.

At the forward end of the window containing missile 156, as shown in FIG. 2, an ogive 201 is releasably fitted in any suitable manner to the casing 193. A separation plate 20-3 may be provided enclosing the space within the ogive 2131 if desired.

The forward end of the window-containing missile 156 is supported at the rearward periphery of its ogive 201 by means of an inner shoulder portion 205 integral with the barrel 133. An O-ring 206 provides a watertight The barrel 133 also has at its forwardmost end a radially outwardly extending fiange 207 which bears against the inside surface of the outer casing 15 of the missile launching unit. As seen also in FIG. 4, the flange 207 has eight equally spaced-apart apertures 208 across each of which is a chordally extending thin rod or hinge 211. From each of the rods 211 there hingeably depends a parachute rod 213 which is of a length of about twothirds the length of the missile casing 193. Each of the rods 213 is suitably sewn or bonded into a parachutetype diaphragm 215 which is made of a soft and easily folded watertight, non-porous material such as rubber or a thin plastic. The lower periphery of the parachute 215 as defined by the circle described by each of the end points of the rods 213 is limited by the size of the lower part of the parachute material, which when extended as shown in FIG. 4, has approximately the shape of a frustocone 217 whose larger upper end meets the periphery formed by the rod ends.

The lower or rearward end of the frusto-conical part 217 of the parachute 215 is watertightly attached as by bonding or welding to the forwardmost inside surface of the chemical cup 135. The top or forwardmost end of the parachute 215 is watertightly attached in any suitable manner to the forwardmost outer surface of the barrel 133 so that the only way water may enter the inner confines of the parachute 215 is from its rearwardmost or lowest end. In order to provide an entry for water, a plurality of holes 219 is drilled into the walls of the chemical casing 135 at its region of greatest diameter, as shown in FIG. 1. Thus the water may enter the bottom of the parachute only through the holes 219. A suitable chemical which reacts with water to produce a gas, such as lithium hydride (LiH) which produces hydrogen (H is located or deposited in the 'forwardmost or upper reaches of the parachute 215 so that when reached by the water, the resulting hydrogen gas forces the water out of the parachute in order to float the missile firing unit after it has been ejected from the outer casing 15.

The parachute bag 215, barrel 133, chemical cup 135, base block 59 and timer casing 57 form a watertight container.

A forward base block 2.21, generally annular in shape and of varying cross section, is mounted in sliding engagement with the forwarclmost inside surfaces of the outer casing 15. The forward base block 221 has a plurality of radial apertures 223, for example, four in number, each extending through the block. The forward base block 221 is held in place in the outer casing 15 by means of radial restraining rods 225 radially movable in sliding engagement in each of the respective apertures 223. The rods 22.5 are shown in FIG. 2 in the positions they normally occupy prior to launching of the missile. The block 221 and rods 225 provide means to block the ejection spring 117 from forcing the missile 156 from the forward end of the casing 15. The outermost ends of the rods 225 are beveled and protrude from each of the apertures 223 into each respective one of a plurality of apertures 227 located in the outer casing normally in register with apertures 223. The inner portion of the forward base block 221 is longitudinally elongated to form a hollow shaft 229 the rearwardmost end of which has a radially inwardly extending shoulder portion 231 thus forming a small axial opening 233. The nose portion of the ogive 201 is urged against the periphery of the opening 233 under the force of the powerful ejection spring 117. The restraining rods 225 themselves have insufficient leverage to hold the forward base block 221 in place against the force of the spring 117. However, if the rods 225 are prevented from being moved inwardly by the cam action of the casing 15 against the outer beveled portions of each of the rods, then the forward base block 221 is held in place thereby.

The rods 225 are normally held in their respective restraining positions by means of a variably shaped plunger 235 slidably mounted for longitudinal movement in the hollow portion of the shaft 229. The plunger is shown in the position it normally occupies prior to launching. The plunger has an axial bore 237 threaded at its aftermost end to receive a water-pressure sensing plug or valve 239. The plug 239 actually serves two purposes: (1) to act as a leak-preventing valve to prevent excess moisture from entering the unit while temporarily stored prior to use, and (2) to control the movements of the plunger 235 responsive to the differential in pressure between the inside and outside of the casing 15.

The outside surface of the plunger 235 has a groove 241 with an inclined rear surface 243. With the plunger 235 in its normally occupied position as shown in FIG. 2, the groove 241 is forward of the positions of each of the rods 225, and the outer surface of the plunger bears against rods 225 preventing any movement thereof.

The plug 239 has an axial bore 245 and a shoulder portion 247 extending inwardly of said bore at the rearwardmost end of the plug. The plug 239 is sealed in the bore 237 by means of an O-ring 249. A fixed pressure-plate 251 is mounted near the forward end of the bore 245 and is separated from a longitudinally movable pressure plate 253 slida bly mounted near the opposite end of the bore by a compression spring 255. An O-ring 257 is positioned between the movable pressure plate 253 and the shoulder 247 so that it is squeezed by the urging of the compression spring 255 to effectively seal the plug 239.

It is understood that the plug 239 prevents the entry of excess atmospheric moisture inside the casing 15 (which would unfortuitously trigger the reaction with the lithium hydride). Moreover, when the pressure on the outside of the casing 15 exceeds by a predetermined amount the pressure of the inside of the casing 15, the plug 239 is forced thereby rearwardly against the plunger 235 so that the plunger, which is slidably mounted, moves rearwardly in the bore 229 of the forward base block 221. During this rearward movement, the recess 241 passes into register with each of the radial apertures 223 thus making possible the inward radial movement of each of the restraining rods 225. Under the forward urging force of the powerful ejection spring 117, the nose or ogive 261 of the missile 156 bears against the shoulder 231 of the base block 221. The resulting camming interaction between the beveled ends of each of the restraining rods 225 and the casing 15 forces each of said rods to withdraw inwardly of the casing apertures 227 so that the base block 221 is released from its blocking position and is pushed forwardly out of the casing 15 along with the now ejecting missile firing unit 13.

In those instances where the unit is to be launched from an initial underwater position, as, for example, from a submarine or other submerged launching station, an attachable subsurface launch control unit 11 shown to the left in FIG. 2, is provided to controllably float and cause the release of the missile unit to a suitable position for launching.

In order to attach the unit 11 to the unit 9, the forward base block 221 is provided at its forward end with an inwardly facing threaded portion 257. The unit 11 has an outer tubular casing 259 cylindrical in shape and having thin walls. At the rear portion of the casing 259 is an inwardly extending relatively thick annular shoulder portion 261 having a rearwardly extending longitudinal portion 263 threaded for receipt into the threaded portion 257 of the forward base block 221 of unit 9.

A collapsible container 265 is slidably mounted inside the casing 259 for longitudinal movement forwardly therein and employs a base support plate 267 having four equally spaced apart apertures 269 therein. A pair of cylindrically shaped half-sleeves 271 are each releasably fitted into the peripheral edge of the base support plate 267 and extend longitudinally forwardly therefrom to a forward end plate 273 into which they are releasably fitted at the peripheral edge thereof. The forward side of the end plate 273 has four equally spaced apart radial flooding grooves 275 extending outwardly from a central recess 277.

A spacer ring 279 of smaller diameter than that of the two half-sleeves is press fitted at its forward edge into the back side of the base support plate 267 and extends rearwardly to hear at its rear edge against the shoulder portion 261. A powerful ejection compression spring 281 is positioned in the space between the outer surface of the spacer ring 279 and the casing 259 and at its back end bears against the shoulder 261 and at its forward end against the portion of the support base plate 267 outward of the spacer ring. A can 253 in the form of a hollow cylinder closed at its forward end is attached by means of a bolt or screw 285 into the rear surface of the base support plate 267, the sides of the can extending rearwardly and rather tightly into a space between the shoulder portion 263 and the forward hollow shaft position of the base block 221. The can 283 protects the pressure-sensitive plug or valve 239 from high pressure transients such as those which might occur in a submarine high pressure discharge tube or as a result of shock loading on the unit.

The container 265 provides a housing for an easily foldable flotation bag 287 made of any suitable non-porous watertight material such as rubber or thin plastic. The bottom of the bag is open so that water may flow thereinto when exposed to water. A quantity of lithium hydride (LiH) 289 is suitably located or deposited inside the bag 287 in its upper reaches so that when it comes in intimate contact with water, it chemically combines therewith to form hydrogen gas which fills the bag 287 and expels water therefrom.

A stabilizing lift bar 291 is attached to the periphery of the bottom opening of the bag 287, and a line 293 extends from the bar 291 through one of the apertures 259 to a hook 295 suitably secured to the base support plate 267.

A circular forward and block 257 fits snugly but releasably inside the forward end of the tubular container 259 and is suitably sealed therewith by means of an O-ring 2%. The forward end block 297 has a central axial bore 301 having a forward portion 303 of greater diameter and a rearward portion 305 of less diameter separated by a shoulder 366. The larger bore portion 323 is occupied by a leak valve 397 primarily to prevent the entry of excess water vapor into the vicinity of the bag 271 causing a premature reaction with the lithium hydride contained therein. The leak valve 307 is rotata bly mounted on a locking arm 309 shown in its locked position and held in place by means of a latch pin 311 combined unit is dropped into the water.

inserted through both the locking arm and a pair of opposed retaining blocks 312.

The leak valve 307 has an axial center rod 315 rigidly connected to a sleeve 317 by means of a disc member 319 so that there is an annular recess therebetween. The sleeve 317 fits tightly but slidably into the large bore portion 305. A spring plate 321 is urged against the disc member 319 by a compression spring 323 surrounding the rear portion of the rod 315, the other end of the Spring 323 being urgingly positioned against a cylindrical spring block 325 of varying cross section. The rearward portion of the spring block 325 is stepped in two adjacent longitudinal locations to form thereby a rod lifting shoulder 327 and a seal-maintaining shoulder 329. The shoulder 32-9 is urged by the compression spring 323 against an O-ring 331 which is in turn compressed between the shoulder 329 and the bore shoulder 306 to provide an effective seal. In a manner similar to the rods 22-5, radial restraining rods 332 beveled at their outer ends are mounted in the block 297 and are shown in the positions they occupy prior to launching. Removal of the leak valve 307 permits the rods 332 to be carried inwardly so that the block 297 may slide out of casing 259.

For launching of the unit from a surface ship, instead of attaching the subsurface control unit 11 to the unit 9, as shown in FIG. 4 a surface firing adaptor unit 333 is attached. The unit 333 includes a threaded 335 having a raised open head 337 and a larger diameter threaded portion 339 which is screwed into the threaded portion of the block 221 in the unit 9. The forward end of the plug 239 is threaded to receive an adaptor plug 341 having a central axial bore 343.

In operation, the timing setting for the launching of the window-containing missile 156 is carried out in the same manner for both surface and subsurface launching. The index ring 27 is rotated to a position as desired opposite the appropriate scale marking of the scale gradations 31. When the index ring 27 is rotated, the knob rotor 21 rotates therewith. Through the cruciate longitudinally slidable linkage of the timer key 33, the timing control shaft 39 is rotated. Since the ball bearings 47 provide rotative connecting linkage between the control shaft 39 and the axial shaft '65 of the timer base plate 63, the timer base plate is also rotated with the control shaft 39, thus rotating counterclockwise the timing bar 93 a circumferential distance away from the microswitch contact arm proportional to the desired elapsed time after ejection of the missile firing unit 13.

It is understood that the timing bar 93 will rotate until the missile firing unit 13 has been ejected from the outer casing 15.

For launching the unit from a surface station, the surface adaptor unit 333 as shown in FIG. 4 is attached as previously described to the unit 9, and the resulting The unit sinks until the difference in pressure between the out side and the inside of the casing 15 is sufiicient to cause the plug 239 to be pushed (due to greater outside water pressure) backward into the bore 229 of the block 221. Water leaks into the interior of the casing 15, and when the differential in pressure on the casing 15 eventually becomes sufilciently small, the ejection spring 117 exerts a forward force so that the restraining rods 225 are cammed inward against the outer casing 15. When said rods entirely withdrawn from the apertures 227, the ejec tion spring 117 forces all of the elements out of the forward end of the tubular casing 15 except the timing and ejection control unit 20. The block 221 falls away under the urging of the forwardly (i.e., upwardly) moving ogive 201. As best seen in FIG. 10, the missile firing unit 13 ejected by the spring 117 includes the timer casing 57, the chemical casing or cup 135, and the barrel 133 including the parachute bag 215 attached thereto. Water 10 leaking into the casing 15 comes into intimate contact with the sea battery and actuates the battery.

As the ejection spring 117 forces the timer casing 157 forwardly out of the outer casing 15, the force of the spring 117 is sufiicient to cause the ball bearings 45 and 47 to be forced by the camming action of the edges of the aperture 43 of the bulbous portion of the shaft 39 into and partially through the larger diameter apertures 69 against the tapered portion 69a thus freeing the timing base plate 63 and its shaft 65 for forward movement under the force of the compression spring 81. When the timing base plate 63 moves forward, the timing bar 93 is moved to a position to strike the contact arm 103 of the microswitch 101. Also, when the plate 63 moves forward, the restraining pin 95 is relatively moved out of engagement with the gear 97 of the clock 83, and the clock commences to run.

During and after the ejection of the missile firing unit 13 from the outer casing 15, water enters through the chemical casing aperture 219 to the bottom of the parachute bag 215 and reaches the lithium hydride located therein to cause the generation of hydrogen gas. The gas expels the water out of the bottom of the parachute bag thus increasing the buoyancy of the unit and causing it to float to the water surface.

Referring to FIGS. 10 and 11, when the unit reaches the surface, it floats thereon until the timing bar 93 strikes the microswitch contact arm 103, thus closing a part of the series circuit of FIG. 5. However, the glow plug 107 is not energized until the mercury level switch 106 is closed by virtue of the unit reaching a level position momentarily on the surface of the water.

When the How plug 107 is energized, the heat therefrom ignites the black powder 127, the explosion when reaching its full force pushing against the push block to cause the breaking of the stud 139 at its narrow portion 145. The explosive force also urges the stud 139 forward to cause the firing pin 153 to ram the pyrotechnic delay line 191. The force of the expanding gases is directed against the push block 155 which urges the window-containing missile 156 forwardly out of the barrel 133 with sufiicient force to lift the missile 156 several hundred feet above the water surface. The altitude attainable by the missile 156 depends upon the amount of explosive force necessary on the push block 155 to break the neck 145.

As the missile 156 is gaining altitude, the pyrotechnic delay line 191 is burning. Its burn rate is suitably adjusted so that when the missile 156 reaches its approxirnate highest point of its trajectory, the black powder in the hollow portion of nut 181 explodes. The resulting expanding gases urge the base plate 195 of the missile 156 forward, said base plate pushing the two half-sleeves 197 forwardly. The radar reflective material, or Window 199 is pushed against the forward plate 203 at the base of the releasably fitted ogive 201 while the half-sleeves 197 also push against the ogive so that the window is ejected from the forward end of the missile 156. The window ejecting phase is best seen in FIG. 12. The two half-sleeves 197, upon exposure to air resistance fall away from the window material, as does the ogive 201, so that said window material is free to disperse under the force of air resistance into the atmosphere.

In the subsurface launching operation, the subsurface control unit 11 is attached as described in conjunction with FIG. 2 to the unit 9, and the timer setting is made in exactly the same manner as previously described for launching from a surface station. As shown in FIG. 6, the latch 311 is then removed and the leak valve 307 is opened. The units 9 and 11 as attached are suitably discharged into the water by means of garbage disposal tubes or the like in the submarine.

With the leak valve 307 removed, water is free to enter the bore 303 and travels via the flooding grooves 275 of the end plate 273 into the interior of the casing 259. The 'water fills the bag 287 through its open but folded bottom and eventually reaches the lithium hydride if 289 contained therein. The resultingly generated hydrogen gas fills up the bag and expels the water therein so that it becomes buoyant to lift the units 9 and 11 upwardly.

At the same time, during the flow of water into the container 259, the pressure differential between the higher sea pressure outside the casing and the lower pressure interior of the casing 259 decreases. Depending upon th rate of flow into the casing, this pressure differential rather rapidly reaches a sufficiently low value so that the ejection spring 281 overcomes the bias of sea pressure tending to force the block 297 into the casing. Under the force of the ejection spring 281, the rods 332 are cammed raidially inwardly and the block 297 is pushed forwardly out of the end of the casing 297. The bag 287, now filling with hydrogen gas so as to expel water out of the bottom thereof, is also ejected from the casing 259 under the force of the spring 231 pushing against the apertured plate 267. This action is best seen in FIGS. 7 and 8 which show the bag 287 when sufficiently buoyant with hydrogen exerting an upward pull via the line 293 on the hook 295 so as to lift the entire units 9 and 11 toward the water surface.

\Vhen the plate 267 is pushed forwardly out of the casing 259, the can 283 is carried therewith. The purpose of the can 283 prior to its ejection was to delay the entry of appreciable amounts of water into the region confined thereby, thus delaying the action of direct water pressure against the longitudinally movable plug 239 of the unit 9. However, with the can 283 now out of the vicinity of the plug 239, the water pressure against the plug 239 forces it rearwardly (as previously explained in conjunction with surface launching operation) so that the restraining rods 225 are free to be cammed inwardly under the force of the powerful ejection spring 117. As the units rise toward the water surface, the water pressure on the block 221 decreases sufficiently so that as shown in FIG. 9, under the force of the spring 117 of the unit 9, the block 221 may then be ejected forwardly out of casing 15. The depth at which ejection occurs, and thus when the clock begins to run, may be adjusted by varying the bevel of rods 225. Since the block 221 is threadedly attached to the unit 11, it is carried away from the vicinity of the ejected missile firing unit 13. The ejected missile firing unit 13 then floats to the water surface under the buoyant lift of the parachute bag 215 and launched in the same manner as previously described in conjunction with surface launching.

It is appreciated that the provision of the subsurface firing control unit 11 attached to the unit greatly enhances the reliability and ease of subsurface launching of the window-containing missile. If the unit 11 were not attached, a sub-surface launching of the unit 9 with only the surface launching adaptor unit of FIG. 3 attached would result in the immediate actuation of the timing clock at a great distance below the water surface. This would cause the premature firing of the unit prior to its attaining a position on the surface of the water.

Obviously, many modifications and variations of the present invention are possible in the light of the above teachings. It is therefore to be understood that within the scope of the appended claims the invention may be practiced otherwise than as specifically described.

What is claimed is:

1. A launching unit for a missile containing material to be dispersed comprising:

an outer tubular container open at one end;

a watertight container for the material-containing missile movably and releasably mounted in said outer container;

water pressure-responsive blocking means releasably mounted in the open end of said outer container for enclosing and holding said watertight missile container therein;

ejection means biasing said watertight missile container and said blocking means for egress from the open end of said outer container;

flotation means having buoyancy producing means becoming buoyant only when exposed to intimate contact with water, for lifting said watertight missile container to the surface of water;

thrust means located in said watertight container for thrusting said material-containing missile above the surface of water only after release of said blocking means;

and adjustable timing means actuatable responsive to egress of said blocking means under the bias of said ejection means, for actuating said thrust means after a preset interval;

whereby when said launching unit is dropped into water said blocking means is released under the force of water pressure and said watertight container is ejected by said ejection means and floats upwardly toward the water surface.

2. Apparatus as defined according to claim 1 but further characterized by said blocking means comprising a block having a central bore;

a centrally bored plunger movable in said block bore;

a plurality of inwardly movable restraining rods each extending through said block to bear against said plunger and protrudingly past its outermost surface to bear against said outer container to prevent movement of said block relative to said outer container;

pressure sensitive means mounted in the central opening of said plunger and bearing thereagainst whereby under external pressure said plunger is moved by said pressure sensitive means to free said movable restraining rods for inward movement thereby permitting relative movement between said block and said outer container.

3. Apparatus as defined according to claim 1 but further characterized by said flotation means comprising a watertight bag open at its lower end and having a quantity of lithium hydride located therein.

4. Apparatus as defined according to claim 1 but further characterized by said thrust means comprising an explosion chamber filled with explosive material for projecting said missile; a glow plug extending into said chamber; a sea battery, switching means connected in series with said glow plug and said sea battery and actuatable responsive to a predetermined condition of said watertight container.

5. Apparatus as defined accoring to claim 1 but further characterized by said ejection means comprising a compression spring urging at one end against the closed end of said outer container and at its other end against said watertight container.

6. A launching unit for a missile containing material to be dispersed into the atmosphere, comprising:

an outer tubular container;

a watertight container for the material-containing missile movably and releasably mounted in said outer container;

flotation means located in said watertight container becoming buoyant when exposed to water;

blocking means for preventing the egress of said watertight container releasably mounted in one end of said outer container;

ejection means biasing said watertight container and the material-containing missile for egress from said one end of said container;

said blocking means normally preventing said egress;

thrust-producing means located in said watertight container for thrusting said material-containing missile above the surface of water;

timing setting means for presetting the time of thrust of said material-containing missile mounted in the other open end of said outer tubular container;

actuating means for energizing said thrust-producing means located in said watertight container; and

means releasably coupling said timing means to said actuating means;

whereby after release between said timing means and said actuating means, said watertight container remains watertight.

7. Apparatus as defined according to claim 6 but further characterized by said timing setting means comprising an index ring settable to a scale;

a rotor connected to said ring and rotatable therewith;

a first link element mounted in said rotor for longitudinal movement within said rotor and rotatable therewith;

a second link element mounted in said first link element for longitudinal movement therein and rotatable therewith;

a central link shaft integral with said second link element; and

said releasable coupling means comprising a central control shaft rotatably and watertightly mounted in said watertight container and having a sleeve portion surrounding a portion of said link shaft;

releasable bearing elements coupling said link shaft and said central shaft for rotation together;

and saidactuating means comprising a clock having a running time proportional to the amount of rotation ofsaid central shaft mounted in said watertight container;

a battery-powered electric circuit for energizing said thrust-producing means; and

switch means coupled to said clock and to said electric circuit for energizing said circuit responsive to a preset running time of said clock.

' 8. Apparatus as defined according to claim 6 but furfor said launching unit comprising a further container open at one end and attached blocking means;

further flotation means located in said further container and becoming buoyant when exposed to intimate contact with water; further blocking means positioned in the open end of said further container for holding and enclosing said furthe'r'flotation means in said further container; further ejection means positioned in said further container normally biasing said flotation and blocking means "for egress from the open end of said further container; said further blocking means being releasable from its blocking position responsive to a sufficiently low differential in pressure between the outside and the inside of said further container whereby said ejection means ejects said further flotation and further blocking means therefrom; and

at its other end to said means connecting said further flotation means to said blocking means of said tubular container for lifting said tubular container toward the surface of water. 9. Water-launched unit for a missile containing material to be dispersed in the atmosphere comprising:

a tubular outer container; 7 an essentially watertight container positioned inside I i ,said outer container, said watertight container havof said outer container for holding said watertight container in said outer container;

pressure-sensitive means coupled to said blocking means for releasing said blocking means from its holding position responsive a predetermined differential in pressure between the outside and the inside of said outer container;

ejection means biasing said blocking means and said watertight container for egress from the other end of said container when said blocking means is released; and

flotation means coupled to said watertight container for lifting said watertight container toward the surface of water when said watertight container is released under the force of said ejection means.

10. Apparatus as defined according to claim 9 but further characterized by said flotation means comprising a watertight bag open only at its lower end and having a quantity of lithium hydride located therein, and means watertightly connecting said bag to said watertight container in surrounding relationship to the upper portion thereof.

11. Appartus as defined according to claim 9 but further characterized by said watertight container having a forward compartment for said missile, a middle portion including an explosion chamber having a quantity of explosive therein for thrusting said missile therefrom when actuated, and a rearward portion containing said actuating means.

12. A water-launched unit for dispersing material into the atmosphere comprising:

an elongated hollow cylindrical missile having a detachable ogive at its forward end and an explosion chamber in its rear portion carrying explosive material therein;

a plurality of discrete sleeve elements mounted around the inside periphery of said missile for longitudinal movement forwardly therefrom;

a longitudinally movable plate supporting said sleeve elements and pushing said elements forwardly under the force of an explosion in said chamber;

a quantity of material-to-be-dispersed located within the confines of said plurality of sleeve elements; an elongated essentially watertight container for said missile having an open forward portion;

means watertightly sealing the ogive portion of said missile releasably into the open forward portion of said watertight container;

said missile being longitudinally movable forward from the open portion of said watertight container;

a chamber having explosive material located therein located in said watertight container;

a push block having a central opening separating said chamber from the rearwardmost end of said missile whereby when the material in said chamber is caused to explode, the missile is thust forwardly by said push block from said watertight container;

a pyrotechnic delay line connecting the rearwardmost end of said missile to the explosion chamber of said missile;

a firing pin sealably but longitudinally movably mounted in the central opening of said push block for ramming into said pyrotechnic delay line responsive to an explosion in the chamber of said watertight container;

actuating means located in said watertight container for causing an explosion in said chamber of said Watertight container; I

an outer tubular container for said watertight container;

time setting means located at one end of said tubular container sealably but releasably coupled to said actuating means for selecting a time of actuation thereof;

15 ejection means positioned in said outer container and biasing said watertight container for egress from the other end of said outer container; blocking means releasably mounted in the other end of said container for enclosing and holding against the bias of said ejection means said watertight container in said outer casing;

pressure-sensitive means coupled to said blocking means for releasing said blocking means from its holding position responsive to a predetermined differential in pressure between the inside and outside of said outer container;

and flotation means coupled to said watertight container for lifting said watertight container toward the water surface when said watertight container is released from the outer container under the force of said ejection means.

13. Apparatus as defined according to claim 12 but further characterized by said ejection means comprising a compression spring urging said watertight container away from said outer casing.

14. Apparatus as defined according to claim 13 but further characterized by said actuating means comprising a clock the running time of which is set by said time setting means, and electrical means energizable responsive to a condition of said clock for causing an explosion in the chamber of said watertight container.

15. Apparatus according to claim 12 wherein said material is radar reflective filamentary material.

16. Apparatus according to claim 12 but further comprising a subsurface fing control unit sealably attachable to said blocking means for delaying the action of said pressure-sensitive means.

17. Apparatus according to claim 16 but further characterized by said subsurface launching control unit comprising means for postponing the reaching of a condition of sufiiciently high pressure on said pressure-sensitive means, to cause said pressure-sensitive means to release said blocking means from its holding position, and further flotation means located in said subsurface launching control unit for lifting said launching and said subsurface launching control units toward the surface of a body of water during said period of postponement.

18. Apparatus according to claim 12 but further characterized by said missile having a plurality of stabilizing fins in its rear external portion.

19. Apparatus as defined according to claim 18 but further characterized by hinge means for rotatably mounting each of said fins, each of said fins being rotatable from a position flush against the external surface of said missile to a position extendnig outwardly from said misile, and resilient means biasing each of said fins toward said outwardly extending positions, said fins being constrained from reaching said outwardly extending positions by an inside surface of said watertight container.

20. Apparatus for launching dispersive material into the atmosphere comprising:

an outer tubular container;

an inner container movable in said outer container and having a watertight portion and an elongated openended barrel portion adjacent thereto and adjacently forward thereof in the direction of said movement; flotation means connected to said inner container;

an elongated missile for carrying dispersive material sealably but releasably mounted for movement from the open end of said barrel portion;

clock actuated thrust-producing means located in the watertight portion of said inner container for thrusting said missile from said barrel responsive to a clock setting; time setting means sealably and rotat-ably mounted to one end of said outer casing and sealably but releasably coupled to the watertight portion of said inner container for presetting the time of actuation of said thrust producing means;

ejection means biasing said inner container for movement from the other end of said outer container; and

pressure-sensitive blocking means releasably mounted in the other end of said outer container for holding said inner container in place in said outer container against the bias of said ejection means until a predetermined differential in pressure between the outside and inside of said outer casing is reached, whereby said blocking means is released to permit the ejection means to expel said inner container from said outer container.

21. Apparatus as defined according to claim 20 but further characterized by a subsurface launching control unit comprising means sealably attachable to said blocking means for delaying the reaching of said predetermined differential in pressure, and further flotation means located in said subsurface launching control unit for lifting both said units upwardly during said period of delay.

22. Apparatus as defined according to claim 20 but further characterized by said thrust producing means comprising:

a cup-shaped element fixedly mounted in said barrel and having a quantity of explosive material disposed therein;

a push block spaced from cupshaped element and said material and movably mounted in said barrel for pushing said elongated missile out of the open end of said barrel responsive to an explosive force produced by said material;

said push block having a central opening;

a stud member extending through said central opening and at one end bearing against said push block for limited movement therewith toward the open end of said barrel;

means rigidly securing said stud member at its other end to said cup-shaped element; v

said stud member having a neck portion of reduced transverse cross sectional area in the space between said push block and said cup-shaped element;

whereby the distance of travel of said missile is proportional to the amount f force necessary to sever said neck portion of the stud member.

23. Apparatus as defined according to claim 22 but further characterized by said neck portion having a smoothly curved shape extending to a region of least transverse cross sectional area of said stud member.

24. Apparatus as defined according to claim 22 wherein said neck portion is located substantially within the confines of the space bounded by said cup-shaped element.

References Cited by the Examiner UNITED STATES PATENTS 421,307 2/1890 Reynolds 891 650,288 5/1900 Wilson 102-7 923,801 6/1909 Bargar 9-321 1,815,226 7/ 193 1 Anderson 102-7 2,487,056 11/1949 King 102-7 2,929,324 3/1960 Berman et a1. 102-13 BENJAMIN A. BORCHELT, Primary Examiner.

SAMUEL \V. ENGLE, Assistant Examiner. 

1. A LAUNCHING UNIT FOR A MISSILE CONTAINING MATERIAL TO BE DISPERSED COMPRISING: AN OUTER TUBULAR CONTAINER OPEN AT ONE END; A WATERTIGHT CONTAINER FOR THE MATERIAL-CONTAINING MISSILE MOVABLY AND RELEASABLY MOUNTED IN SAID OUTER CONTAINER; WATER PRESSURE-RESPONSIVE BLOCKING MEANS RELEASABLY MOUNTED IN THE OPEN END OF SAID OUTER CONTAINER FOR ENCLOSING AND HOLDING SAID WATERTIGHT MISSILE CONTAINER THEREIN; EJECTION MEANS BIASING SAID WATERTIGHT MISSILE CONTAINER AND SAID BLOCKING MEANS FOR EGRESS FROM THE OPEN END OF SAID OUTER CONTAINER; FLOTATION MEANS HAVING BUOYANCY PRODUCING MEANS BECOMING BUOYANT ONLY WHEN EXPOSED TO INTIMATE CONTACT WITH WATER, FOR LIFTING SAID WATERTIGHT MISSILE CONTAINER TO THE SURFACE OF WATER; THUS MEANS LOCATED IN SAID WATERTIGHT CONTAINER FOR THRUSTING SAID MATERIAL-CONTAINER MISSILE ABOVE THE SURFACE OF WATER ONLY AFTER RELEASE OF SAID BLOCKING MEANS; AND ADJUSTABLE TIMING MEANS ACTUATABLE RESPONSIVE TO EGRESS OF SAID BLOCKING MEANS UNDER THE BIAS OF SAID EJECTION MEANS FOR ACTUATING SAID THRUST MEANS AFTER A PRESET INTERVAL; WHEREBY WHEN SAID LAUNCHING UNIT IS DROPPED INTO WATER SAID BLOCKING MEANS IS RELEASED UNDER THE FORCE OF WATER PRESSURE AND SAID WATERTIGHT CONTAINER IS EJECTED BY SAID EJECTION MEANS AND FLOATS UPWARDLY TOWARD THE WATER SURFACE. 